前 言 拦截卫星的末制导阶段具有下列特点,即速度非常高,受重力场影响以及机动控制是采用推力而不是用空气动力。然而,卫星弹道的距离预计要超过飞行器的距离,因为飞行器在地球大气层里运动。尽管如此,系统的误差预计还会存在。弹道中段和（或）发射制导系统本身的精确度也还有限,因此,末制导显然是很需要的。 本文采用了末制导规律。 INTRODUCTION The terminal guidance phase of intercepting satellites has the characteristics of being very high, being affected by the gravitational field, and using maneuvering instead of aerodynamics. However, the trajectory of the satellite is expected to exceed the distance of the aircraft because the aircraft is moving in the Earth's atmosphere. In spite of this, systematic errors are expected to exist. The accuracy of the ballistic mid-launch and / or launch guidance system itself is also limited, so that final guidance is obviously needed. This article uses the guidance of the end of the law.